前缘尖化对飞翼布局飞行器气动隐身性能影响
作者:
作者单位:

1.军委装备发展部某中心,北京 100034;2.北京机电工程研究所,北京 100074;3.航天工程大学宇航科学与技术系,北京 101416

作者简介:

通讯作者:

洪苇江,男,工程师,E-mail:honwj@qq.com。

中图分类号:

V221.3

基金项目:


Influence of Sharp Leading Edge on Aerodynamic Stealth Performance of Flying-Wing Aircraft
Author:
Affiliation:

1.A Center of Armaments Development of the Central Military Commission, Beijing 100034, China;2.Beijing Institute of Mechanical and Electical Engineering, Beijing 100074, China;3.Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China

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    摘要:

    飞翼布局飞行器内翼段前缘尖化可降低雷达回波的镜面反射强度,进而提升隐身性能。针对前缘尖化可能带来的气动问题,本文对一种典型飞翼布局飞行器的流场和电磁散射特性开展了模拟仿真。以RANS方程作为控制方程,采用k-ω SST湍流模型求解,对全机气动性能进行了分析,并结合流场特征作出解释。采用多层快速多极子算法,在典型入射频率下对全机电磁散射特征开展仿真计算。结果表明,对飞翼布局飞行器内翼段开展前缘尖化修形,可有效缩减前向雷达散射截面(Radar cross section,RCS),增加突防能力,但可能会同时带来起降条件下失速迎角减小等问题。通过选取适当的前缘尖化范围,该情况可得到改善,从而具备工程化应用条件。

    Abstract:

    For flying-wing aircraft, the sharpening of the leading edge of the inner wing section can reduce the intensity of the specular reflection of the radar echo, thereby improving the stealth performance. Aiming at the aerodynamic problems caused by the sharpening of the leading edge, simulations are carried out on the flow field and electromagnetic scattering characteristics of a typical flying-wing aircraft. RANS equation is used as the governing equation, and the k-ω SST turbulence model is used to solve the problem. The aerodynamic performance of the flying-wing aircraft is analyzed, and the flow field characteristics are combined to explain. Using the multi-layer fast multipole algorithm, the simulation calculation of the electromagnetic scattering characteristics is carried out under the typical incident frequency. The results show that the leading edge sharpening modification of the inner wing section of the flying-wing layout aircraft can effectively reduce the forward radar cross section (RCS) and increase the penetration capability. But at the same time, it will bring about problems such as reduction of stall angle of attack under takeoff and landing conditions. By selecting an appropriate leading edge sharpening range, the situation can be improved, so as to have engineering application conditions.

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引用本文

洪苇江,李小婷,薛晖,杨乐,杨道宁.前缘尖化对飞翼布局飞行器气动隐身性能影响[J].南京航空航天大学学报,2022,54(2):245-252

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历史
  • 收稿日期:2020-08-26
  • 最后修改日期:2021-04-17
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  • 在线发布日期: 2023-02-22
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